Airworthiness Directives; Airbus Model A319, A320, and A321 Airplanes, 33661-33663 [E6-9061]

Download as PDF Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules (2) For any inspection done after the effective date of this AD: Within 30 days after the inspection. Parts Installation (l) As of the effective date of this AD, no person may install, on any airplane, any sliding tube, or MLG shock absorber having a sliding tube installed, if the sliding tube has a S/N identified in the service information, unless the sliding tube has been inspected, and any applicable corrective actions have been done, in accordance with paragraph (g)(2)(i), (h), or (i) of this AD. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (n) French airworthiness directive F–2005– 115, dated July 6, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on May 31, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–9062 Filed 6–9–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24990; Directorate Identifier 2006–NM–013–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). wwhite on PROD1PC61 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This proposed AD would require an inspection to determine if the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, and repair if necessary. This proposed AD results from cases of girt bar disengagement from the floor fitting during deployment tests of slide rafts at the forward passenger doors. We are proposing this AD to prevent VerDate Aug<31>2005 20:57 Jun 09, 2006 Jkt 208001 disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane. DATES: We must receive comments on this proposed AD by July 12, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24990; Directorate Identifier 2006–NM–013–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 33661 comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A319, A320, and A321 airplanes. The DGAC advises that, during deployment tests of slide rafts at the forward passenger doors, cases of girt bar disengagement from the floor fitting were reported. Investigations have demonstrated that the girt bar disengagements were due to incorrect position of the stiff part of the girt bar during installation of the slide raft on airplanes. This may cause inboard-directed loads on the girt bar, preventing a correct engagement in the floor fittings. This condition, if not corrected, could result in disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane. Relevant Service Information Airbus has issued Service Bulletin A320–25–1394, Revision 01, dated December 12, 2005. The service bulletin describes procedures for a general visual inspection to determine whether the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, and repair if necessary. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005– E:\FR\FM\12JNP1.SGM 12JNP1 33662 Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules 172 on December 21, 2005, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Costs of Compliance This proposed AD would affect about 719 airplanes of U.S. registry. The proposed actions would take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $57,520, or $80 per airplane. wwhite on PROD1PC61 with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the VerDate Aug<31>2005 20:57 Jun 09, 2006 Jkt 208001 national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. deployment tests of slide rafts at the forward passenger doors. We are issuing this AD to prevent disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection and Repair Comments Due Date (a) The FAA must receive comments on this AD action by July 12, 2006. (f) Within 200 days after the effective date of this AD, do a general visual inspection to determine if the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 25–1394, Revision 01, dated December 12, 2005. If the stiff part of the girt or the girt bar position is incorrect, before further flight, repair in accordance with the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (g) Inspecting and repairing if necessary before the effective date of this AD in accordance with Airbus Service Bulletin A320–25–1394, dated July 23, 2004, is acceptable for compliance with the requirements of paragraph (f) of this AD. Affected ADs (b) None. Alternative Methods of Compliance (AMOCs) Applicability (c) This AD applies to Airbus Model A319, A320, and A321 airplanes, certificated in any category; on which Airbus Modification 20233, 25902, or 24365 (installation of slide raft) has been done in production; excluding those airplanes having manufacturer’s serial numbers 1794, 2155, 2195, 2204, 2231, 2239, 2244, 2246, 2247, 2252, 2254, 2255, 2257, 2259, 2261, 2263, 2267, 2273, 2274, 2275, 2278, 2280, 2282, 2284, 2286, 2288, 2297, 2301, 2307, 2310, 2314, 2327, 2369, and subsequent. (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Unsafe Condition (d) This AD results from cases of girt bar disengagement from the floor fitting during (i) French airworthiness directive F–2005– 172, issued December 21, 2005, also addresses the subject of this AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–24990; Directorate Identifier 2006–NM–013–AD. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Related Information E:\FR\FM\12JNP1.SGM 12JNP1 Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Proposed Rules Issued in Renton, Washington, on May 31, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–9061 Filed 6–9–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24999; Directorate Identifier 2006–NM–060–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–10 and DC–10– 10F Airplanes; and Model MD–10–10F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). wwhite on PROD1PC61 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas Model DC– 10–10 and DC–10–10F airplanes; and Model MD–10–10F airplanes. This proposed AD would require replacing the clamp bases for the fuel vent pipe with improved clamp bases. This proposed AD results from reports that the foil wrapping on existing plastic clamp bases has migrated out of position, which compromises the bonding of the fuel vent pipes to the airplane structure. We are proposing this AD to ensure that the fuel vent pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, and create an ignition source, which could result in a fuel tank explosion. DATES: We must receive comments on this proposed AD by July 27, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. VerDate Aug<31>2005 20:57 Jun 09, 2006 Jkt 208001 • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Serj Harutunian, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5254; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24999; Directorate Identifier 2006–NM–060–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 33663 level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (67 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination E:\FR\FM\12JNP1.SGM 12JNP1

Agencies

[Federal Register Volume 71, Number 112 (Monday, June 12, 2006)]
[Proposed Rules]
[Pages 33661-33663]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9061]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24990; Directorate Identifier 2006-NM-013-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A319, A320, and A321 airplanes. This proposed 
AD would require an inspection to determine if the stiff part of the 
girt and girt bar position of the forward left-hand and right-hand 
passenger doors is incorrect, and repair if necessary. This proposed AD 
results from cases of girt bar disengagement from the floor fitting 
during deployment tests of slide rafts at the forward passenger doors. 
We are proposing this AD to prevent disengagement of the telescopic 
girt bar from the airplane when the door is opened in emergency 
situations, which could result in the inability to open the passenger 
door and to use the escape slide/raft at that door during an emergency 
evacuation of the airplane.

DATES: We must receive comments on this proposed AD by July 12, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24990; Directorate Identifier 2006-NM-013-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A319, A320, and A321 
airplanes. The DGAC advises that, during deployment tests of slide 
rafts at the forward passenger doors, cases of girt bar disengagement 
from the floor fitting were reported. Investigations have demonstrated 
that the girt bar disengagements were due to incorrect position of the 
stiff part of the girt bar during installation of the slide raft on 
airplanes. This may cause inboard-directed loads on the girt bar, 
preventing a correct engagement in the floor fittings. This condition, 
if not corrected, could result in disengagement of the telescopic girt 
bar from the airplane when the door is opened in emergency situations, 
which could result in the inability to open the passenger door and to 
use the escape slide/raft at that door during an emergency evacuation 
of the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A320-25-1394, Revision 01, dated 
December 12, 2005. The service bulletin describes procedures for a 
general visual inspection to determine whether the stiff part of the 
girt and girt bar position of the forward left-hand and right-hand 
passenger doors is incorrect, and repair if necessary. Accomplishing 
the actions specified in the service information is intended to 
adequately address the unsafe condition. The DGAC mandated the service 
information and issued French airworthiness directive F-2005-

[[Page 33662]]

172 on December 21, 2005, to ensure the continued airworthiness of 
these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously.

Costs of Compliance

    This proposed AD would affect about 719 airplanes of U.S. registry. 
The proposed actions would take about 1 work hour per airplane, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $57,520, or $80 
per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-24990; Directorate Identifier 2006-NM-
013-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 12, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319, A320, and A321 
airplanes, certificated in any category; on which Airbus 
Modification 20233, 25902, or 24365 (installation of slide raft) has 
been done in production; excluding those airplanes having 
manufacturer's serial numbers 1794, 2155, 2195, 2204, 2231, 2239, 
2244, 2246, 2247, 2252, 2254, 2255, 2257, 2259, 2261, 2263, 2267, 
2273, 2274, 2275, 2278, 2280, 2282, 2284, 2286, 2288, 2297, 2301, 
2307, 2310, 2314, 2327, 2369, and subsequent.

Unsafe Condition

    (d) This AD results from cases of girt bar disengagement from 
the floor fitting during deployment tests of slide rafts at the 
forward passenger doors. We are issuing this AD to prevent 
disengagement of the telescopic girt bar from the airplane when the 
door is opened in emergency situations, which could result in the 
inability to open the passenger door and to use the escape slide/
raft at that door during an emergency evacuation of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection and Repair

    (f) Within 200 days after the effective date of this AD, do a 
general visual inspection to determine if the stiff part of the girt 
and girt bar position of the forward left-hand and right-hand 
passenger doors is incorrect, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-25-1394, Revision 01, 
dated December 12, 2005. If the stiff part of the girt or the girt 
bar position is incorrect, before further flight, repair in 
accordance with the service bulletin.
    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''
    (g) Inspecting and repairing if necessary before the effective 
date of this AD in accordance with Airbus Service Bulletin A320-25-
1394, dated July 23, 2004, is acceptable for compliance with the 
requirements of paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (i) French airworthiness directive F-2005-172, issued December 
21, 2005, also addresses the subject of this AD.


[[Page 33663]]


    Issued in Renton, Washington, on May 31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-9061 Filed 6-9-06; 8:45 am]
BILLING CODE 4910-13-P

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